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Low Earth orbits (LEO) are known as a region of high space activity and,consequently, space debris highest density. Launcher upper stages and defunctsatellites are the largest space debris objects, whose collisions can result instill greater pollution, rendering further space missions in LEO impossible.Thus, space debris mitigation is necessary, and LEO region is a primary targetof active debris removal (ADR) projects. However, ADR planning requires atleast an approximate idea of the candidate objects' attitude dynamics, which isone of the incentives for our study. This paper is mainly focused on modelingand simulating defunct satellites. The model takes into account the gravitygradient torque and the torque due to eddy currents induced by the interactionof conductive materials with the geomagnetic field. A better understanding ofthe intermediate phase of the exponential deceleration is achieved owing to amore accurate model of the eddy currents torque than in most prior research. Wealso show the existence of other important factors in the studied dynamics suchas evolution of the orbit itself and the residual magnetic moment, which bothcontribute to the overall attitude motion evolution and the variety of thefinal regimes.

Defunct Satellites in Nearly Polar Orbits: Long-term Evolution of Attitude Motion